Thrust vectoring apparatus for maneuvering missile in flight

Abstract

Thrust vectoring apparatus for a missile for imparting bank and pitch to missile for maneuvering it in flight. The missile is provided with a generally rectangular jet exhaust opening in which is pivotally mounted a pair of two-dimensional plugs which define a plug nozzle for the opening. The plugs, disposed on opposite sides of a vertical longitudinal plane of the missile, are adapted to be selectively and independently pivoted in response to a control mechanism acting in response to guidance command signals for banking and pitching the missile for maneuvering it in flight.

What is claimed is: 
     
       1. In a jet exhaust propelled missile, associated thrust vectoring apparatus for imparting bank and pitch to the missile for maneuvering it in flight, comprising: wall means defining a jet exhaust opening of generally rectangular cross section;   plug means disposed within the jet exhaust opening for defining a plug nozzle therein;   said plug means comprising a pair of generally two-dimensional plugs pivotally mounted in side-by-side adjacency on axes extending across the rectangular jet exhaust opening; and   means responsive to guidance commands for selectively pivoting each plug independently about its axis for vectoring thrust of jet exhaust gasses passing through the defined plug nozzle;   whereby, when the plugs are pivoted in opposite directions, the missile is caused to bank about its longitudinal extent, and when the plugs are both pivoted in the same direction the missile is caused to pitch about an axis transverse to its longitidinal extent thereby providing maneuvering of the missile in flight.   
     
     
       2. The invention according to claim 1 wherein the pair of plugs are coaxially mounted. 
     
     
       3. The invention according to claim 2 wherein the pair of plugs are pivotally mounted on shaft means supported from walls which define the jet exhaust opening. 
     
     
       4. The invention according to claim 1 wherein the plugs are tear-drop shaped. 
     
     
       5. The invention according to claim 4 wherein the tear-drop shaped plugs are truncated at their downstream extremities. 
     
     
       6. The invention according to claim 2 wherein the plugs in addition to defining the nozzle further define turning vanes in the jet exhaust gases to provide moment on the missile. 
     
     
       7. The invention according to claim 2 wherein the plugs are located on opposite sides of a longitudinal axis of the missile. 
     
     
       8. A jet exhaust propelled missile having thrust vectoring apparatus for improved maneuvering characteristics in flight, comprising: wall means defining a rearwardly directed generally rectangular jet exhaust gas opening;   said rearwardly directed opening equally disposed on opposite sides of a vertical plane which bisects the missile and extends longitudinally of the missile and contains the longitudinal axis thereof;   plug means disposed between the walls defining the generally rectangular jet exhaust gas opening for defining a plug nozzle between the plug means and the wall means for the passage of exhaust gases therethrough;   said plug means comprising a pair of generally two-dimensional tear drop shaped plugs each pivotally mounted in side-by-side adjacency on axes extending laterally across the opening;   said plugs disposed on opposite sides of the vertical plane;   means responsive to guidance commands for selectively pivoting each plug independently about its axis for vectoring thrust of the jet exhaust gases passing through the plug nozzle;   whereby, when the plugs are pivoted to opposite directions, thrust vectoring of the exhaust gases cause the missile to roll about its longitudinal axis for imparting a bank thereto; and, when the plugs are both pivoted in the same direction, thrust vectoring of the exhaust gases causes the missile to pitch about an axis tranverse to the vertical plane for maneuvering the missile in flight.   
     
     
       9. The invention according to claim 8 wherein the generally rectangular jet exhaust gas opening has a dimension along one side which is approximately twice that along another side. 
     
     
       10. The invention according to claim 9 wherein the jet exhaust gas opening is disposed with its greater dimension lying transversely of the vertical plane. 
     
     
       11. An improved arrangement for maneuvering a missile in flight, comprising: a frame defining a rectangular opening for missile exhaust gases disposed on either side of a plane established vertically of an elongate missile body and containing its longtudinal axis;   a pair of two-dimensional plugs positioned in side-by-side adjacency within the frame opening and disposed respectively on opposite sides of the plane to define a plug nozzle for exhaust gases passing therethrough;   said plugs pivotally mounted on axes extending across the frame opening and normal to the vertical plane;   said plugs adapted for independent pivotal positioning about their axes in response to missile guidance commands for vectoring exhaust gases passing through the nozzle;   whereby, when the plugs are pivoted to opposite directions, thrust vectoring of the exhaust gases causes the missile to roll about its longitudinal axis for imparting a bank thereto; and, when the plugs are both pivoted in the same direction, thrust vectoring of the exhaust gases causes the missile to pitch about an axis transverse to the vertical plane for maneuvering the missile in flight.